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公开(公告)号：US10760423B2
公开(公告)日：2020-09-01
申请号：US15947119
申请日：2018-04-06
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Stephen P. Muron , Ioannis Alvanos , Christopher M. Dye , Brian D. Merry , Arthur M. Salve, Jr. , James W. Norris
Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk at an interface, where the interface is defined along a spoke. A spool for a gas turbine engine includes the rotor disk, the plurality of blades with the interface defined along the spoke radially inboard of a blade platform, a rotor ring axially adjacent to the rotor disk, and a plurality of core gas path seals which extend from the rotor ring. Each of the plurality of core gas path seals extends from the rotor ring at a seal interface, with the seal interface defined along a spoke and the plurality of core gas path seals being axially adjacent to the blade platform.
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公开(公告)号：US10458249B2
公开(公告)日：2019-10-29
申请号：US15033933
申请日：2014-11-05
Applicant: United Technologies Corporation
Inventor： Michael G. McCaffrey , Ioannis Alvanos , Michael G. Abbott , Grant O. Cook, III
Abstract: An airfoil component includes a first segment that has a first piece of a mount and a first piece of an airfoil. The first segment is formed of a first ceramic-based material. A second segment includes a second piece of the mount and a second piece of the airfoil. The second segment is formed of a second ceramic-based material. The first and second segments are bonded together along a bond joint such that the first and second pieces of the mount are bonded to each other and the first and second pieces of the airfoil are bonded to each other.
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公开(公告)号：US20190153866A1
公开(公告)日：2019-05-23
申请号：US15819047
申请日：2017-11-21
Applicant: United Technologies Corporation
Inventor： Dmytro Mykolayovych Voytovych , Alexander Staroselsky , Om P. Sharma , Gabriel L. Suciu , Brian Merry , Ioannis Alvanos
Abstract: An exemplary gas turbine engine includes a turbine section and a fan mechanically connected to the turbine section such that rotation of the turbine drives rotation of the fan. The fan includes a hub, a plurality of blade bodies extending radially outward from the hub to a first partial shroud, and a plurality of blade tips extending radially outward from the partial shroud.
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公开(公告)号：US20180230909A1
公开(公告)日：2018-08-16
申请号：US15947890
申请日：2018-04-09
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Ioannis Alvanos , Brian D. Merry
CPC classification number: F02C7/20 , F01D9/041 , F01D25/30 , F02K1/04 , F05D2300/6033 , Y02T50/672 , Y02T50/673 , Y10T29/4932
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a turbine case extending along a turbine axis and a CMC turbine exhaust case mounted to the turbine case. The CMC turbine exhaust case includes a CMC core nacelle aft portion, a CMC tail cone connected to the CMC core nacelle aft portion, and a multiple of CMC turbine exhaust case struts extending between the CMC core nacelle aft portion and the CMC tail cone. The CMC core nacelle aft portion, the CMC tail cone and the turbine case are arranged along the turbine axis. The CMC turbine exhaust case is mounted to the turbine case at a flange such that the CMC tail cone is axially spaced apart from the turbine case relative to the turbine axis.
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公开(公告)号：US20180223693A1
公开(公告)日：2018-08-09
申请号：US15424930
申请日：2017-02-06
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian Merry , Ioannis Alvanos
CPC classification number: F01D25/30 , F01D9/02 , F02C3/04 , F02K1/04 , F02K1/48 , F02K3/06 , F05D2240/14 , F05D2260/96 , F05D2300/6033 , Y02T50/672
Abstract: A turbine exhaust assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a turbine exhaust case comprised of CMC material and attachable to a turbine case, a tail cone comprised of CMC material that has a leading edge and a trailing edge, and an exhaust mixer comprised of CMC material and coupled to the turbine exhaust case. The exhaust mixer has a plurality of lobes arranged about the tail cone to define an exhaust flow path. A plurality of struts extend from the tail cone to support the exhaust mixer at a location aft of the leading edge of the tail cone. A method of assembling a propulsion system is also disclosed.
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Patent Agency Ranking
公开(公告)号：US20170175633A1
公开(公告)日：2017-06-22
申请号：US15445521
申请日：2017-02-28
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Ioannis Alvanos , Brian Merry
CPC classification number: F02C7/20 , B64D27/10 , B64D27/26 , B64D2027/262 , B64D2027/266 , F05D2220/323 , F05D2230/60 , F05D2240/90 , Y02T50/44 , Y10T29/49947
Abstract: A method for mounting a gas turbine engine having a compressor section, a combustor section, a turbine section, a pylon and a rear mount bracket, includes positioning the mounting bracket between the gas turbine engine and the pylon. The mounting bracket is connected to the turbine case reacting a least a vertical load, a side load, a thrust load, and a torque load from the gas turbine engine through the mounting bracket. The mounting bracket is attached to the pylon reacting the same loads from the gas turbine engine.
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公开(公告)号：US20160290149A1
公开(公告)日：2016-10-06
申请号：US15036019
申请日：2014-11-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James D. Hill , Gabriel L Suciu , Brian D. Merry , Ioannis Alvanos
CPC classification number: F01D11/005 , F01D5/06 , F01D5/081 , F01D9/041 , F01D11/001 , F05D2220/32 , F05D2240/57 , F05D2240/80 , F05D2260/30 , Y02T50/676
Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine. The engine includes a first rotor disk, a second rotor disk, and a circumferentially segmented seal. The segmented seal engages the first rotor disk and the second rotor disk. The segmented seal further includes a fore surface contacting the first disk, an aft surface contacting the second disk, and a radially outer surface. Further, (1) the aft surface and (2) one of the fore surface and the radially outer surface include perforations to allow fluid to flow through the interior of the segmented seal.
Abstract translation: 本公开的一个示例性实施例涉及燃气涡轮发动机。 发动机包括第一转子盘，第二转子盘和周向分段密封件。 分段密封件接合第一转子盘和第二转子盘。 分段密封件还包括接触第一盘的前表面，接触第二盘的后表面和径向外表面。 此外，（1）后表面和（2）前表面和径向外表面中的一个包括穿孔以允许流体流过分段密封件的内部。
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公开(公告)号：US10808622B2
公开(公告)日：2020-10-20
申请号：US16047634
申请日：2018-07-27
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Ioannis Alvanos , Brian Merry
Abstract: A method for mounting a gas turbine engine having a compressor section, a combustor section, a turbine section, a pylon and a rear mount bracket, includes positioning the mounting bracket between the gas turbine engine and the pylon. The mounting bracket is connected to the turbine case reacting a least a vertical load, a side load, a thrust load, and a torque load from the gas turbine engine through the mounting bracket. The mounting bracket is attached to the pylon reacting the same loads from the gas turbine engine.
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公开(公告)号：US10550699B2
公开(公告)日：2020-02-04
申请号：US14773200
申请日：2014-02-13
Applicant: United Technologies Corporation
Inventor： Ioannis Alvanos
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotor having a pretrench that receives at least a portion of a tip of a stator, the portion of the tip extending radially into the pretrench.
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公开(公告)号：US10287905B2
公开(公告)日：2019-05-14
申请号：US15036019
申请日：2014-11-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James D. Hill , Gabriel L Suciu , Brian D. Merry , Ioannis Alvanos
Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine. The engine includes a first rotor disk, a second rotor disk, and a circumferentially segmented seal. The segmented seal engages the first rotor disk and the second rotor disk. The segmented seal further includes a fore surface contacting the first disk, an aft surface contacting the second disk, and a radially outer surface. Further, (1) the aft surface and (2) one of the fore surface and the radially outer surface include perforations to allow fluid to flow through the interior of the segmented seal.
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